Can Smart Materials Modify Blade Root Boundary Conditions to Attenuate Helicopter Vibration?

The feasibility studies of a new solution for the individual blade control aiming at helicopter vibration reduction are performed. Adaptive material actuators are installed at the blade root to induce both a constant pitch, and a constant flap angle in the structure. The results indicate that small angles compatible with the present technology of smart materials are sufficient to produce a significant attenuation in the dynamic response of a typical rotor in forward flight